Cooling system configurations for an aircraft having hybrid-electric propulsion system

ABSTRACT

A cooling system for an engine of an aircraft of a having hybrid-electric propulsion system including a nacelle body including a bottom cooling air intake disposed below a propeller hub for supplying air to an oil-air cooler, wherein the bottom cooling air intake includes a splitter dividing the bottom cooling air intake into a first channel and a second channel.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims priority to U.S. Provisional Patent ApplicationNo. 62/812,479 filed Mar. 1, 2019 the contents of which are incorporatedby reference herein in their entirety.

BACKGROUND Technological Field

The subject invention is directed to a cooling system for an aircraftengine, and more particularly, to cooling system configurations for theengine e of an aircraft having a hybrid-electric propulsion system.

Description of Related Art

The level of air traffic continues to increase worldwide, leading toincreased fuel consumption and air pollution. Consequently, efforts areunderway to make aircraft more environmentally compatible through theuse of specific types of fuel and/or by reducing fuel consumptionthrough the use of more efficient drive systems.

For example, aircraft having mixed drive systems that include acombination of various types of engines are known for reducingpollutants and increasing efficiency. Some current combinations includereciprocating engines and jet engines, reciprocating engines and rocketengines, jet engines and rocket engines, or turbojet engines and ramjetengines.

While these mixed drive systems are useful, they are not readilyadaptable for use on commercial passenger aircraft. However,hybrid-electric propulsion systems that provide power through acombustion engine and an electric motor are indeed adaptable for usewith commercial passenger aircraft and can provide efficiency benefitsincluding reduced fuel consumption. The subject invention is directed toan aircraft having such a propulsion system. The conventional methodsand systems have generally been considered satisfactory for theirintended purpose. However, there is still a need in the art for acooling system having improved efficiency and decreased size envelope.The present disclosure may provide a solution for at least one of theseremaining challenges.

SUMMARY OF THE INVENTION

A cooling system for a nacelle of an aircraft of a havinghybrid-electric propulsion system includes a nacelle body defining andincluding a nacelle of an aircraft of a having hybrid-electricpropulsion system can include a nacelle body including a bottom coolingair intake disposed below a propeller hub for supplying air to anoil-air cooler, wherein the bottom cooling air intake includes asplitter dividing the bottom cooling air intake into a first channel anda second channel, wherein the splitter is vertically or horizontallyaligned. The splitter can form three separate channels, with the firstchannel leading to a first heat exchanger, and the second channelleading to a second heat exchanger, and a third channel leading to aturbine compressor assembly, wherein the first heat exchanger is anair-oil heat exchanger, and the second heat exchanger is a glycol airheat exchanger. It is also conceived that wherein the splitter can behorizontally aligned forming two separate channels, with the firstchannel leading to a first heat exchanger, and the second channelleading to a second heat exchanger, where the first heat exchanger is anair-oil heat exchanger, and the second heat exchanger is a glycol airheat exchanger.

An aircraft can include the purging and cooling system mentioned aboveattached to an underside of a first wing of the aircraft. An aircraftcan include the purging and cooling system mentioned above attached toboth wings. The nacelle body can also include a heat motor enginetherein and an electric motor therein connected to power a propeller.

These and other features of the systems and methods of the subjectdisclosure will become more readily apparent to those skilled in the artfrom the following detailed description of the preferred embodimentstaken in conjunction with the drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

So that those skilled in the art to which the subject inventionappertains will readily understand how to make and use the devices andmethods of the subject invention without undue experimentation,preferred embodiments thereof will be described in detail herein belowwith reference to certain figures, wherein:

FIG. 1 is a perspective view of a cooling system configuration of anengine nacelle of an aircraft having hybrid-electric propulsion system;

FIG. 2a is a perspective view of FIG. 1, showing the inner portions ofthe cooling system;

FIG. 2b is an alternate embodiment of FIG. 1, showing the heatexchangers slimmed and angled;

FIG. 2c is an a top view of FIG. 2b , showing the heat exchangersangled;

FIG. 3a is a perspective view of FIG. 1, showing the nacelle doors in anopen position;

FIG. 3b is a side view of FIG. 1, showing the nacelle doors in an openposition;

FIG. 3c is a side view of FIG. 2b , showing the nacelle doors in an openposition with the heat exchangers attached to the cowls;

FIG. 4a is a perspective view of a cooling system with a horizontalsplitter;

FIG. 4b is a side view of FIG. 4a , showing two channels leading to twodifferent heat exchangers;

FIG. 5a is a front view a system with a horizontal splitter, showing twochannels leading to two different heat exchangers, and a channel leadingto a turbine compressor assembly;

FIG. 5b is a perspective view FIG. 5a of a cooling system with avertical splitter.

DETAILED DESCRIPTION

Reference will now be made to the drawings wherein like referencenumerals identify similar structural features or aspects of the subjectinvention. For purposes of explanation and illustration, and notlimitation, a partial view of an exemplary embodiment of a coolingsystem in accordance with the invention is shown in FIGS. 1a and 1b andis designated generally by reference character 100. Other embodiments ofthe cooling system in accordance with the invention, or aspects thereof,are provided in FIGS. 2a-5b , as will be described.

As seen in FIG. 1, a cooling system 100 for a nacelle of an aircraft ofa having hybrid-electric propulsion system includes a nacelle body 102,a first side cooling air intake 104 disposed on a first side of thenacelle body 102 and a second side cooling air intake 106 disposedopposite the first side cooling air intake with a propeller hub 105disposed therebetween, and a bottom cooling air intake 108 disposedbelow propeller hub 105 for supplying air to an oil-air cooler. Thebottom cooling air intake 108 is elongated in a direction from the firstside cooling air intake and the second side cooling air intake.

Further seen in FIG. 1, the first side cooling air intake 104 and thesecond side cooling air intake 106 each include an inlet defining anarea elongated in a vertical direction with respect to gravity and anoutlet 107 aft of the duct inlet, which includes a variable exhaust areacontrolled by an exhaust access door 207 configured for controlling abypass for the cooling air. By partially closing the exhaust access door207, the intake air is forced to spill over, resulting in less drag andless cooling air being supplied to the nacelle cooler. When the doorsare opened further, more air is able to flow into each of the ducts, andin turn supply air to the heat exchangers. The first side cooling airintake 104 and the second side cooling air intake 106 can each beconnected to a glycol/air heat exchanger 120 for cooling thehybrid-electric propulsion system, shown in FIG. 2.

An aircraft includes the cooling system 100 mentioned above attached toan underside of a first wing 130 of the aircraft. An aircraft caninclude the cooling system mentioned above attached to both wings. Thenacelle body 102 includes a heat motor engine therein and an electricmotor therein connected to power a propeller 105.

Shown in FIG. 2a , a turbine compressor intake 110 is disposed above thebottom cooling air intake 108 and below the propeller 105 for supplyingair to the compressor turbine assembly 109. It is also conceived that abottom cooling air intake 108 is not necessary. The turbine compressorintake 110 is concentrically connected to the compressor turbineassembly 109 located inside the nacelle body 102. A glycol cooler andtwo oil coolers are disposed within the nacelle body 102. FIGS. 2b and2c show the glycol/air heat exchangers 120 slimmed and angled todecrease the profile of the nacelle.

As seen in FIGS. 3a and 3b , the glycol/air heat exchangers 120 can besecured in place and not move along with the cowl doors 122, when thecowl doors 122 are opened for maintenance. It is also considered, Asseen in FIG. 3c , the side heat exchangers can be attached to each ofthe nacelle cowls, which can be hingedly attached to the nacelle body102, wherein the nacelle access doors allow for drip testing when placedin the open position. The cowls can swing open such that the engine orengines are exposed to the ground with allowing any fluids excreted bythe engine or engines to reach the ground.

Referring to FIGS. 4a - and 4 b, a cooling system for a nacelle of anaircraft of a having hybrid-electric propulsion system can include anacelle body 102 including a bottom cooling air intake 410 disposedbelow a propeller hub 405 for supplying air to an oil-air cooler,wherein the bottom cooling air intake includes a horizontal splitter 412dividing the bottom cooling air intake into a first channel and a secondchannel. As seen in FIGS. 4a and 4b the horizontal splitter 412 formstwo separate channels, with the first channel 490 leading to a firstheat exchanger 492, and the second channel 491 leading to a second heatexchanger 493, where the first heat exchanger 492 is an air-oil heatexchanger, and the second heat exchanger 493 is a glycol air heatexchanger.

As seen in FIGS. 5a and 5, a vertical splitter 414 can form threeseparate channels which lead to different air intakes and different heatexchangers. The splitter can form three separate channels 510, 511, and512, with the first channel 510 leading to a first heat exchanger, thesecond channel 511 leading to a second heat exchanger, and a thirdchannel 512 leading to a turbine compressor assembly, wherein the firstheat exchanger 492 is an air-oil heat exchanger, and the second heatexchanger 493 is a glycol air heat exchanger.

It is further envisioned that the heat motor of the system describedabove could be a heat engine of any type, e.g., a gas turbine, sparkignited, diesel, rotary or reciprocating engine of any fuel type andwith any configuration of turbomachiney elements, either turbocharger,turbo supercharger, supercharger and exhaust recovery turbo compounding,either mechanically, electrically, hydraulically or pneumaticallydriven. An example of a rotary engine suitable for this application isdisclosed in U.S. Pat. No. 10,145,291, the disclosure of which is hereinincorporated by reference in its entirety.

The methods and systems of the present disclosure, as described aboveand shown in the drawings, provide for electrical power system withsuperior properties including increased reliability and stability, andreduced size, weight, complexity, and/or cost. While the apparatus andmethods of the subject disclosure have been showing and described withreference to embodiments, those skilled in the art will readilyappreciate that changes and/or modifications may be made thereto withoutdeparting from the spirit and score of the subject disclosure.

What is claimed is:
 1. A cooling system for an engine of an aircrafthaving hybrid-electric propulsion system comprising: a nacelle bodydefining and including a first side cooling air intake disposed on afirst side of the nacelle body and a second side cooling air intakedisposed opposite the first side cooling air intake with a propeller hubdisposed therebetween; and a bottom cooling air intake disposed belowpropeller hub for supplying air to an oil-air cooler, wherein a turbinecompressor assembly intake is disposed above the bottom cooling airintake and below the propeller hub for supplying air to the compressorturbine assembly.
 2. The cooling system of claim 1, wherein the turbinecompressor assembly air intake is concentrically connected to adownstream turbine located inside the nacelle body.
 3. The coolingsystem of claim 1, wherein the first side cooling air intake and thesecond side cooling air intake each include a duct inlet defining anarea elongated in a vertical direction with respect to gravity.
 4. Thecooling system of claim 3, wherein the first side cooling air intake andthe second side cooling air intake each include an outlet aft of theduct inlet.
 5. The cooling system of claim 3, wherein each outletincludes a variable exhaust area controlled by an exhaust access doorconfigured for controlling a bypass for the cooling air.
 6. The coolingsystem of claim 4, wherein the bottom cooling air intake is elongated ina direction from the first side cooling air intake and the second sidecooling air intake.
 7. The cooling system of claim 1, wherein the firstside cooling air intake and the second side cooling air intake are eachfluidly connected to a glycol/air heat exchanger for cooling thehybrid-electric propulsion system.
 8. The cooling system of claim 1,wherein the first side heat exchanger is attached to a nacelle cowlhingedly attached to the nacelle body.
 9. The cooling system of claim 8,wherein the cowl allows for drip testing when placed in the openposition.
 10. The cooling system of claim 1, wherein a glycol cooler andtwo oil coolers are disposed within the nacelle body.
 11. The coolingsystem of claim 1, wherein the first side cooling air intake includes aheat exchanger therein, wherein in the heat exchanger is located outsideof the nacelle body.
 12. An aircraft including the cooling system ofclaim 1 attached to a first wing of the aircraft.
 13. The aircraft ofclaim 12, wherein the cooling system of claim 1 is attached to a secondwing of the aircraft.
 14. The aircraft of claim 12, wherein the coolingsystem of claim 1 is attached to a first wing of the aircraft whereinthe nacelle body includes heat motor engine therein and an electricmotor therein connected to power a propeller.
 15. An aircraft includingthe cooling system of claim 1, wherein the nacelle body is attached toan underside of a wing of the aircraft.